NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 22112 (naca22112-jf) Reynolds number: 1,000,000 Max Cl/Cd: 89.45 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca22112-jf-1000000.txt Download as CSV file: xf-naca22112-jf-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 22112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7853 0.09033 0.08856 -0.0070 1.0000 0.0141
-12.750 -1.0224 0.04287 0.03989 -0.0341 1.0000 0.0135
-12.500 -1.0625 0.03695 0.03351 -0.0301 1.0000 0.0136
-12.250 -1.0731 0.03414 0.03042 -0.0263 1.0000 0.0138
-12.000 -1.0690 0.03220 0.02825 -0.0239 1.0000 0.0139
-11.750 -1.0772 0.02807 0.02370 -0.0205 1.0000 0.0142
-11.500 -1.0633 0.02680 0.02235 -0.0189 1.0000 0.0144
-11.250 -1.0451 0.02613 0.02164 -0.0177 1.0000 0.0146
-11.000 -1.0260 0.02554 0.02102 -0.0166 1.0000 0.0148
-10.750 -1.0071 0.02477 0.02017 -0.0155 1.0000 0.0150
-10.500 -0.9887 0.02379 0.01909 -0.0142 1.0000 0.0152
-10.250 -0.9697 0.02282 0.01802 -0.0130 1.0000 0.0155
-10.000 -0.9506 0.02179 0.01687 -0.0117 1.0000 0.0157
-9.750 -0.9312 0.02076 0.01572 -0.0104 1.0000 0.0160
-9.500 -0.9113 0.01983 0.01468 -0.0091 1.0000 0.0163
-9.250 -0.8911 0.01905 0.01379 -0.0077 1.0000 0.0166
-9.000 -0.8706 0.01844 0.01310 -0.0064 1.0000 0.0168
-8.750 -0.8534 0.01720 0.01175 -0.0045 1.0000 0.0172
-8.500 -0.8352 0.01635 0.01086 -0.0028 1.0000 0.0176
-8.250 -0.8153 0.01590 0.01041 -0.0013 1.0000 0.0179
-8.000 -0.7955 0.01551 0.01000 0.0003 1.0000 0.0183
-7.750 -0.7759 0.01516 0.00963 0.0019 1.0000 0.0187
-7.500 -0.7566 0.01480 0.00924 0.0036 1.0000 0.0191
-7.250 -0.7365 0.01441 0.00882 0.0052 0.9999 0.0196
-7.000 -0.7025 0.01392 0.00829 0.0038 0.9983 0.0201
-6.750 -0.6691 0.01326 0.00758 0.0026 0.9963 0.0206
-6.500 -0.6360 0.01250 0.00682 0.0012 0.9945 0.0214
-6.250 -0.6020 0.01214 0.00647 -0.0001 0.9921 0.0221
-6.000 -0.5681 0.01177 0.00609 -0.0014 0.9890 0.0229
-5.750 -0.5328 0.01140 0.00571 -0.0030 0.9864 0.0237
-5.500 -0.4965 0.01116 0.00546 -0.0047 0.9839 0.0244
-5.250 -0.4674 0.01052 0.00481 -0.0051 0.9776 0.0257
-5.000 -0.4352 0.01023 0.00454 -0.0059 0.9716 0.0267
-4.750 -0.4069 0.00997 0.00427 -0.0058 0.9617 0.0278
-4.500 -0.3787 0.00976 0.00403 -0.0056 0.9509 0.0287
-4.250 -0.3534 0.00937 0.00361 -0.0049 0.9375 0.0302
-4.000 -0.3276 0.00918 0.00341 -0.0042 0.9219 0.0318
-3.750 -0.3015 0.00903 0.00322 -0.0035 0.9044 0.0334
-3.500 -0.2755 0.00887 0.00299 -0.0028 0.8851 0.0347
-3.250 -0.2499 0.00866 0.00273 -0.0021 0.8636 0.0373
-3.000 -0.2235 0.00857 0.00257 -0.0016 0.8409 0.0397
-2.750 -0.1972 0.00845 0.00236 -0.0010 0.8137 0.0429
-2.500 -0.1710 0.00839 0.00220 -0.0004 0.7803 0.0467
-2.250 -0.1448 0.00835 0.00204 0.0001 0.7443 0.0522
-2.000 -0.1181 0.00827 0.00189 0.0005 0.7140 0.0622
-1.750 -0.0975 0.00727 0.00154 0.0016 0.6890 0.2719
-1.500 -0.0752 0.00658 0.00137 0.0024 0.6628 0.4322
-1.250 -0.0509 0.00625 0.00130 0.0031 0.6362 0.5296
-1.000 -0.0254 0.00605 0.00125 0.0037 0.6112 0.5975
-0.750 0.0005 0.00594 0.00123 0.0042 0.5873 0.6496
-0.500 0.0265 0.00584 0.00123 0.0047 0.5628 0.6999
-0.250 0.0526 0.00582 0.00123 0.0052 0.5362 0.7416
0.000 0.0789 0.00582 0.00125 0.0057 0.5095 0.7768
0.250 0.1052 0.00583 0.00129 0.0062 0.4851 0.8102
0.500 0.1315 0.00587 0.00134 0.0068 0.4607 0.8403
0.750 0.1575 0.00593 0.00140 0.0074 0.4369 0.8687
1.000 0.1843 0.00604 0.00146 0.0079 0.4111 0.8858
1.250 0.2111 0.00618 0.00152 0.0082 0.3845 0.8996
1.500 0.2378 0.00634 0.00160 0.0086 0.3585 0.9125
1.750 0.2645 0.00649 0.00167 0.0090 0.3345 0.9248
2.000 0.2912 0.00668 0.00177 0.0094 0.3099 0.9351
2.250 0.3180 0.00686 0.00187 0.0098 0.2858 0.9447
2.750 0.3728 0.00730 0.00210 0.0102 0.2373 0.9610
3.000 0.4002 0.00753 0.00222 0.0104 0.2172 0.9686
3.250 0.4311 0.00776 0.00236 0.0097 0.1994 0.9732
3.500 0.4637 0.00799 0.00251 0.0087 0.1848 0.9771
3.750 0.4948 0.00819 0.00266 0.0080 0.1741 0.9818
4.000 0.5291 0.00840 0.00281 0.0066 0.1652 0.9841
4.250 0.5655 0.00859 0.00296 0.0047 0.1588 0.9854
4.500 0.6010 0.00882 0.00314 0.0030 0.1516 0.9871
4.750 0.6363 0.00896 0.00328 0.0013 0.1478 0.9891
5.000 0.6703 0.00916 0.00344 -0.0001 0.1434 0.9914
5.250 0.7028 0.00942 0.00367 -0.0012 0.1379 0.9939
5.500 0.7386 0.00955 0.00381 -0.0030 0.1354 0.9950
5.750 0.7740 0.00970 0.00397 -0.0047 0.1322 0.9963
6.000 0.8086 0.00990 0.00414 -0.0063 0.1287 0.9978
6.250 0.8423 0.01021 0.00442 -0.0078 0.1235 0.9993
6.500 0.8722 0.01032 0.00456 -0.0083 0.1220 1.0000
6.750 0.8949 0.01045 0.00471 -0.0073 0.1199 1.0000
7.000 0.9173 0.01061 0.00487 -0.0063 0.1172 1.0000
7.250 0.9394 0.01081 0.00506 -0.0053 0.1143 1.0000
7.500 0.9602 0.01113 0.00537 -0.0040 0.1103 1.0000
7.750 0.9832 0.01125 0.00552 -0.0031 0.1089 1.0000
8.000 1.0060 0.01140 0.00570 -0.0022 0.1068 1.0000
8.250 1.0286 0.01159 0.00589 -0.0012 0.1041 1.0000
8.500 1.0507 0.01184 0.00612 -0.0002 0.1010 1.0000
8.750 1.0723 0.01215 0.00644 0.0009 0.0977 1.0000
9.000 1.0958 0.01230 0.00663 0.0016 0.0959 1.0000
9.250 1.1190 0.01251 0.00685 0.0024 0.0932 1.0000
9.500 1.1415 0.01277 0.00710 0.0033 0.0900 1.0000
9.750 1.1634 0.01313 0.00746 0.0042 0.0864 1.0000
10.000 1.1874 0.01332 0.00769 0.0048 0.0844 1.0000
10.250 1.2108 0.01359 0.00797 0.0054 0.0814 1.0000
10.500 1.2332 0.01395 0.00832 0.0061 0.0777 1.0000
10.750 1.2565 0.01426 0.00867 0.0068 0.0750 1.0000
11.000 1.2799 0.01456 0.00899 0.0073 0.0719 1.0000
11.250 1.3020 0.01498 0.00939 0.0080 0.0682 1.0000
11.500 1.3245 0.01536 0.00980 0.0086 0.0654 1.0000
11.750 1.3469 0.01574 0.01020 0.0093 0.0622 1.0000
12.000 1.3673 0.01628 0.01073 0.0101 0.0581 1.0000
12.250 1.3894 0.01667 0.01116 0.0108 0.0556 1.0000
12.500 1.4094 0.01721 0.01170 0.0116 0.0522 1.0000
12.750 1.4290 0.01776 0.01228 0.0125 0.0490 1.0000
13.000 1.4482 0.01832 0.01286 0.0135 0.0459 1.0000
13.250 1.4652 0.01902 0.01357 0.0147 0.0427 1.0000
13.500 1.4830 0.01960 0.01420 0.0158 0.0403 1.0000
13.750 1.4964 0.02041 0.01502 0.0174 0.0374 1.0000
14.000 1.5096 0.02108 0.01574 0.0192 0.0354 1.0000
14.250 1.5203 0.02192 0.01662 0.0211 0.0332 1.0000
14.500 1.5287 0.02295 0.01769 0.0230 0.0311 1.0000
14.750 1.5397 0.02386 0.01866 0.0245 0.0297 1.0000
15.000 1.5470 0.02507 0.01993 0.0261 0.0281 1.0000
15.250 1.5510 0.02662 0.02154 0.0276 0.0265 1.0000
15.500 1.5593 0.02793 0.02293 0.0285 0.0255 1.0000
15.750 1.5641 0.02963 0.02471 0.0293 0.0244 1.0000
16.000 1.5652 0.03181 0.02696 0.0298 0.0233 1.0000
16.250 1.5623 0.03458 0.02982 0.0298 0.0223 1.0000
16.500 1.5650 0.03697 0.03232 0.0295 0.0216 1.0000
16.750 1.5634 0.03999 0.03544 0.0288 0.0209 1.0000
17.000 1.5574 0.04374 0.03931 0.0275 0.0203 1.0000
17.250 1.5466 0.04833 0.04401 0.0256 0.0198 1.0000
17.500 1.5301 0.05390 0.04972 0.0231 0.0194 1.0000
17.750 1.5076 0.06056 0.05652 0.0199 0.0192 1.0000
18.000 1.4796 0.06822 0.06435 0.0162 0.0191 1.0000
18.250 1.4465 0.07683 0.07313 0.0120 0.0191 1.0000
18.500 1.4091 0.08637 0.08285 0.0074 0.0193 1.0000
18.750 1.3673 0.09680 0.09347 0.0023 0.0195 1.0000
19.000 1.3252 0.10755 0.10439 -0.0029 0.0198 1.0000
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